Suspended water-launched missile



April 27, 1965 J. E. DRAIM SUSPENDED I WATER-LAUNCHED MISSILE 2Sheets-Sheet 1 Filed April 29, 1963 Fig. 5

INVENTOR Q JOHN EMERY DRAIM A TTORNEY April 27, 1965 J. E. DRAIM v3,180,225

SUSPENDED WATER-LAUNCHED MI S S ILE Filed April 29, 1963 2 Sheets-Sheet.2

t/IO m AVE AMPLITUDE DEPTH OF WATER INVENTOR. E PROF'LE JOHN EMERY DRAIMF! g. 9 BY ATTORNEY United States Patent 3,180,225 SUSPENDEDWATER-LAUNCHED MISSILE John Emery Draim, Sanford, Fla., assignor to theUnited States of America as represented by the Secretary of the NavyFiled Apr. 29, 1963, Ser. No. 277,416 8 Claims. (Cl. 891.7 (Grantedunder Title 35, US. Code (1952), see. 266) The invention describedherein may be manufactured and used by or for the Government of theUnited States of America for governmental purposes without the paymentof any royalties thereon or therefor.

This application is a continuation-in-part of application Serial No.72,805, filed November 30, 1960, now abandoned for SuspendedWater-Launched Rocket Vehicle.

The present invention relates to an apparatus including a suspendedwater-launched missile and more particularly to amissile which islaunchedfrom a body of water while it is suspended below the surface ofthe water so as to attain launching stability.

The present method of launching large payloads into earth-centeredorbits or deep-spaced missions is from a land based facility requiringexpensive support equipment costing three to five times as much as themissile itself. The present invention eliminates equipment such as fueland oxidizer storage facilities, cryogenic systems, concrete launchingpads, large steel gantries and armoured block houses by providing anapparatus wherein a missile can be launched from water. The seas enable70% of the earths surface to become a potential launch site since themissile can be towed or carried literally anywhere therein as describedin a US. Patent No. 3,077,143. Phenomenal safety is inherent in awater-launched missile since any explosion due to a malfunctioning ofthe missile will be absorbed 'by the surrounding water, therebyeliminating injuries to personnel and eliminating replacement orrepairing of support equipment; According to the invention the mass ofwater surrounding the sides of a waterlaunched missile will act assemi-rigid launch rails replacing all of the above equipment requiredfor a land launch.

The present invention contemplates launching a missile by freelysuspending it entirely below the surface of the water so as to minimizethe eifect of wave action on the missile prior to launch. Thedepth ofsuspension is, of course, variable depending upon the magnitude of the3,l8tl,225 Patented Apr. 27, 1965 "ice these forces will be lessened andthe missile will have improved stability over a missile floating at thesurface of the water.

The invention further contemplates that the missile will be suspendedfrom a buoyant member which is floating at the surface of the Water andthat at or near the time of firing this buoyant member will be releasedfrom the missile. Still further, the invention contemplates dampeningvertical motion of the missile by attaching a plate dampener to theexhaust end of the missile which can be released from the missile at ornear the time of firing. While suspended the missile will have goodlaunching stability and after firing the. missile will ascend withincreasing velocity toward the surface of the water, thus spending arelatively short period of time at or near the surface of the waterwhere the wave motion is located. Accordingly, the launching stabilityof the suspended missile will be improved over the launching stabilityof a missile launchedfrom a floating position at the surface of thewater. I

An object of the present invention is to provide an apparatus wherein amissile can be launched from a body wave action at the surface of thewater. The proper depth can be easily determined if the amplitude of thewave action at the surface of the water is known. When the wave lengthis small compared to the depth, which is a typical condition of mostlocations at sea, the wave action diminishes rapidly from the surfacedownwards. Thus, at a depth equal to a wave length thediminution of waveamplitude is eor of the amplitude of the wave at the surface(Hydrodynamics, page 366 by Sir Horace Lamb, Dover Press, 1945). In FIG.9 there is shown a wave profile of a troohoidal ocean wave having a wavelength of 500 ft., a wave height of 20 ft., a wave depth of 1000 ft.,and a state 6 sea (winds of 40 knots). The profile characterizes wavemotion as a series of circular motions which rapidly decreaseexponentially with increasing depth. Sincethe wave decay with increasingdepth is exponential, it is apparent that a missile floating at thesurface of the water as described in US. Patent No. 3,077,143 would besubjected to maximum rolling moments because of the differential inforces existing between an upper portion of the missile at the surfaceof of water with improved stability.

Another object is to provide an apparatus wherein a missile can bestably launched from a body of water regardless of the degree of wavemotion of the water.

A further object is to provide an apparatus wherein a missile can bestably launched from the high seas in which normal depths and high seastates are encountered.

Still a further object is to provide an apparatus wherein. p a missilewill have improved vertical stability in a body of Water.

Yet another object is to provide a method of launching a missile from abody of Water with improved stability.

Other objects and many of the attendant advantages of this inventionwill be readily appreciated as the disclosure is made in the .followingdetailed description of a preferred embodiment of the invention asillustrated in the accompanying sheet of the drawing in which:

FIG. 1 is a side view of the apparatus with the missile suspended withina body of water.

FIG. 2 is'a side view of the missile being fired while susupended in thewater.

FIG. 3 is a side view of the missile ascending in the water after beingfired.

FIG. 4 is a side view of the missile commencing its journey into space.

FIG. 5 is an enlarged cross-sectional side View of the noseend of themissile.

FIG. 6 is a view taken along line VIVI of FIG. 5.

FIG. 7 is an enlarged side view of the nozzle end of the missile withthe rocket nozzle and dampener plate shown in cross section.

FIG. 8 is a view taken along VIII-VII[ of FIG. 7; and

FIG. 9 is a wave profile of a trochoidal ocean wave.

, Referring now to the drawings wherein like reference numeralsdesignate like or corresponding parts throughout the several views,there is shown in FIG. 1 an apparatus including a rocket powered missile10 which is suspended directly within and below the surface of a body ofwater by a spherical shaped inflated balloon 12, the latter beingconstructed of a light-weight resilient material such as thin rubber.The. missile 10 is connected to the balloon 12 by a line 14, an upperend of which is attached to a pad 16 molded within the balloon 12 and alower end of which is attached to the nose end of the missile. The lowerend of the line is attached to the missile by a bulb 18 located within areleasable connector 20.

The releasable connector 20 is divided into a lower part 22 which ispress fitted in a plug 24 and an upper part 26 which is slidably mountedwithin the plug 24 and skin 28 of the missile 10. The upper part 26 andthe lower part 22 are connected together by a membrane retainer 31), thelatter being threaded by sectors of threads 31 into each part and havinga thinned medial portion 32. The retainer 30 will be fractured at thethinned portion 32 when an explosive charge 34 is ignited by an igniter36. The fracture of the retainer 30 breaks the threaded connectionbetween the upper part 26 and the lower part 22 causing the upper part26 to slidably disengage the missile 19. In order to prevent anysideways explosion upon the ignition of the explosive charge 34, theupper part 26 is provided with ports 38 which will allow gases of theexplosive charge to escape in an upward direction.

The igniter 36 is electrically connected to a receiver atcuator 40 bylead wires 42, the receiver actuator 40 sending an electrical pulse tothe igniter 36 when a proper signal is received from a transmitter (notshown). A rocket igniter 44 for igniting a rocket motor (not shown) iselectrically connected to the receiver actuator 40 by lead wires 46 andreceives an electrical pulse from the receiver actuator 40 when thelatter receives the signal from the transmitter thereby causing therocket igniter 44 and the igniter 36 to be operated simultaneously.

As shown in FIG. 7, a circular plate dampener 48 has a circular flangeor collar 50 which is releasably connected to a rocket nozzle 52 of themissile by a membrane retainer 54, the latter being threaded by sectorsof threads 55 into both the flange 50 and the rocket nozzle 52. Uponignition of the igniter 44 the rocket motor is fired and exhauststhrough the rocket nozzle 52 to fracture the membrane retainer 54 at athinned medial portion 56. This causes separation of the rocket nozzle52 and the plate dampener 48 by breaking the threaded connectiontherebetween. The dampener plate 48 is provided with a circular opening58 so as to allow the rocket exhaust gases to exhaust downwardly andthus pervent any sideways explosion. The plate 48 is to extend adesigned distance beyond the sides of the missile 10 to provide adesired dampening action.

In order that the missile 10 will be suspended within the water it isrequired that all of that portion of the apparatus (including themissile 10) that is connected to the balloon 12 have an aggregatespecific gravity greater than one with respect to the water. In someembodiments the missile 10 will have a specific gravity greater than onewhereas in other embodiments the weight of the dampening plate 48 orsome other component will be required to be added to the missile toprovide an aggregate specific gravity greater than one.

The line 14 is to have a length which is suflioient to suspend themissile it) in a completely submerged state (as shown in FIG. 1) withthe nose end of the missile located a predetermined distance below thesurface of the water and the nozzle end of the missile spaced above thebottom of the body of water. The suspension of the missile any depthbelow the surface of the water will, of course, increase the stabilityof the missile, however, in the preferred embodiment the line 14 is tohave a length such that the missile 10 is suspended at a depth where thewave motion in the water will have substantially no effect on launchingstability of the missile 10.

In the operation of the device, the missile 10 is freely suspendeddirectly in the water by the balloon 12 to the predetermined depth belowthe surface of the water as shown in FIG. 1. If there is a heavy wavemotion or a heavy sea state at the surface of the water, the missilewill be suspended at a greater depth, whereas when the wave motion orthe sea state is slight at the surface of the water the missile can besuspended at a lesser depth below the surface of the water. Assuming alaunch of the missile at sea and that the wave length and Wave amplitudeof a surface wave are known, the wave amplitude at a depth equal to thesurface wave length, can be found by multiplying the surface waveamplitude by e or Knowing the length of the missile, the Wave amplitudestherealong can be determined for a particular suspended depth, andfurther knowing the upward force component due to the line 14 on themissile the combination of these forces will be determinative indesigning a proper depth. Assuming a length of 40 ft. of the missile anda state 6 sea, an ordinary missile would be suspended at a depth of ft.below the surface of the water in order to insure -a practical andstable suspended condition. Of course, another factor bearing on thedepth required for stability is the type of guidance system employed bythe missile. When the guidance system has a maximum allowableinclination before becoming erratic this must be considered as a designfactor.

After the missile 10 is suspended at the proper depth and it is time forlaunching, the transmitter sends a signal to energize thereceiver/actuator 40, whereupon the receiver/actuator sends anelectrical current simultaneously to the igniter 36 and the rocketigniter 44, the igniter 36 causing the explosive charge to separate theline 14 from the missile and the igniter 44 causing the rocket motor tobe fired. The firing of the rocket motor causes the plate dampener 48 tobe separated from the rocket nozzle 52 by the fracture of the membraneretainer 54. While the missile 10 has been operated by a transmitter, itis to be understood that other means may be employed, such as running adirect line to the missile. Further, while the line 14 is released fromthe missile, the rocket motor is firedand the dampener plate 48 isreleased all substantially simultaneously, it is further to beunderstood that these steps can be done at different intervals. Forinstance, the line 14 and dampener plate could each be separated by aseparate explosive squib at various intervals before the firing of therocket motor.

After the rocket motor is fired the missile ascends vertically in thewater as shown in FIG. 3 and breaks through i the surface of the waterto commence its journey into space as shown in FIG. 4. It is to be notedthat since the missile 10 assumes a dynamic condition upon firing thatits stability will be maintained as it transcends that portion of thewater having wave motion. Since the balloon 12 is constructed of alight-weight resilient material, there will be no effect on thestability of the missile as it breaks the water if it shouldaccidentally strike the balloon. To insure that the line 14 and the pad16 within the balloon 12 do not affect the stability of the missile, ifcontact should be made, the former should be constructed of a flexiblematerial such as manila and the latter should be constructed of aresilient material such as rubber.

Neglecting the weight of the balloon 12 and the line 14, the amount ofwater to be displaced to suspend the missile below the surface of thewater can be easily found by using the formula where V =volume of waterdisplaced by a submerged portion of the balloon in cubic feet S =averagespecific gravity of the missile V =volume of the missile in cubic feetIf a spherical balloon 12 is used as described in the preferredembodiment, it is desirable that the portion of the balloon above theWater have a volume less than 25% of the total volume of the balloon sothat the balloon will provide a good vertical stability (that is, itwill not readily follow the wave motion at the surface of the water).Many other various-shaped buoyant members can be used in lieu of theballoon. For instance, a vertically disposed elongated buoyant memberwith the line 14 attached at one end thereof would be very effective inmaintaining vertical stability of the missile since the lateraldistribution of such a buoyant member with respect to the surface of thewater would be small compared to the vertical distribution of thebuoyant member. If the lateral distribution is in order of 1:1 withrespect to the vertical distribution, good vertical stability can stillbe maintained if the volume of the portion of the buoyant member abovethe water is small (in the order of with respect to the total volume ofthe buoyant member. Regardless of the type of buoyant member used, thevertical stability of the suspended missile will be improved by theplate damper 48 which resists vertical movement of the missile in thewater.

While the specification describes the missile 10 as being propelled by arocket motor it is to be understood that the term missile is to includeany reaction type of power plant such'as solid or liquid rocket, jet,ram jet or nuclear power.

While the specification describes the missile as being connected to theballoon 12 by the line 14 it is to be understood that the missile 10could in some instances be connected directly to the balloon 12 withoutthe use of the line 14.

The reference in this specification to suspending the missile 10 at adepth where wave motion will have substantially no effect on launchingstability means that the missile is suspended at a depth where theparameter-s for the launch are not exceeded, these parameters beinggoverned by the characteristics of the missile such as the maximumallowable inclination dictated by the guidance system upon launch.

It is now apparent that the invention provides a simple device forlaunching a missile from water regardless of the severity of the Wavemotion at the surface of the water. There are many other inherentadvantages such as built-in safety. Should there be a malfunctioning 'orexplosion of the missile, its force would be contained below the surfaceof the Water and thereby would not endanger nearby surface ships.Obviously many modifications and variations of the present invention arepossible in light of the aboveteachings. For instance, the release ofthe line 14 from the missile could be accomplished by providing aweakened portion in the line near the missile. It is therefore to beunderstood that within the scope of the appended claims the inventionmay be practiced otherwise than as specifically described.

I claim: 7

1. An apparatus comprising:

(a) a reaction powered missile which is to be launched from a body ofWater having Wave motion;

(b) said missile having a nose end and an exhaust nozzle end;

(0) a buoyant member having sufiicient buoyancy to float the entireapparatus in the water with a portion of the buoyant member extendingabove the surface of the water;

(d) means connecting said missile to said buoyant member; said meansincluding a member which is releasably mounted in said missile; saidmember adapted to be forcibly expelled from said missile upon launchthereof;

(e) all of that portion of the apparatus which is connected to saidbuoyant member having an aggregate specific gravity greater than onewith respect to the water;

(f) said means for connecting being capable of supporting the missile ina freely suspended position directly within the water with the nose endabove the nozzle end;

(g) said position being at a depth where the nose end is a predetermineddistance below the surface of the water and the nozzle end is spacedabove the bottom of the body of water; and

(h) the missile when suspended being at a depth where the wave motionwill have substantially no effect on its launching stability, wherebyprior to launch and while suspended the missile has suflicient stabilityfor launch, and upon launch the missile assumes a dynamic condition tomaintain its stability while transcending that portion of the body ofwater having wave motion. 7,

2. An apparatus comprising:

(a) a reaction powered missile capable of being launched from a body ofwater having wave motion;

(b) said missile having a nose end and an exhaust nozzle end;

(0) a buoyant member connected to said missile and having suflicientbuoyancy for supporting the missile in a freely suspended position inthe water;

(d) all that part of the apparatus supported by the buoyant memberhaving an aggregate specific gravity greater than one with respect tothe water;

(e) said position being at a depth where the nose end is a predetermineddistance below the surface of the water and the nozzle end is spacedabove the bottom of the body of water;

(1) the missile when suspended being at a depth where the wave motionwill have substantially no effect on its launching stability; 7

(g) means connected to and extending transverse the missile beyond itssides for dampening vertical movement of the missile when suspended inthe water; said means adapted to be forcibly separated from said missileupon launch thereof; said means having a passage therein to provide fordispersion of gases generated upon launch of the missile; and

(h) means for expelling the dampening means upon firing the missile,whereby prior to launch and while suspended the missile has suflicientstability for launch, and upon launch the missile assumes a dynamiccondition sutficient to maintain its stability while transcending thatportion of the body of water having wave motion;

3. An apparatus comprising:

(a) a reaction powered missile which is to be launched from a body ofwater having wave motion;

(b) said missile having a nose end and an exhaust nozzle end;

(0) a buoyant member having sufiicient buoyancy to float the entireapparatus in the water with a portion of the buoyant member extendingabove the surface of the water;

(d) a flexible line connecting said missile to said buoy ant member;

(e) all of that portion of the apparatus which is connected by said lineto the buoyant member having an aggregate speciflic gravity greater thanone with respect to the water;

(f) said line being capable of supporting the missile an aggregatespecific gravity greater than one with water with the nose end above thenozzle end;

(g) said line having a length which is capable of positioning the noseend a predetermined distance below the surface of the water with thenozzle end spaced above the bottom of the body of water; said line beingreleasably attached to said missile through a member slidably mountedtherein; said member adapted to be forcibly expelled from said missileupon launch thereto;

(11) the length of said line further being such that the missile will besuspended at a depth where wave motion will have substantially no effecton launching stability of the missile, whereby prior to launch and whilesuspended the missile has suflicient stability for launch, and uponlaunch the missile assumes a dynamic condition to maintain its stabilitywhile transcending that portion of the body of water having wave motion.

4. An apparatus comprising:

(a) a reaction powered missile which is to be launched from a body ofwater having wave motion;

(b) said missile having a nose end and an exhaust nozzle end;

(c) a buoyant member having sufficient buoyancy to float the entireapparatus in the water with a portion of the buoyant member extendingabove the' surface of the water;

(d) means connecting said missile to said buoyant member; 7 i

() all of that portion of the apparatus which is connected to saidbuoyant member having an aggregate specific gravity greater than onewith respect to the water;

( said means for connecting being capable of supporting the missile in afreely suspended position directly within the water with the nose endabove the nozzle end; said means including a member slidably mounted insaid missile; said member adapted to be forcibly expelled from saidmissile upon launch thereof; and

(g) said position being at a depth where the nose end is a predetermineddistance below the surface of the water and the nozzle end is spacedabove the bottom of the body of water;

(h) the missile when suspended being at a depth where the wave motionwill have substantially no efifect on its launching stability;

(i) means for firing the missile when suspended at said depth; and

(j) means for expelling the buoyant member from the missile upon firing,whereby prior to launch and while suspended the missile has sufficientstability for launch, and upon launch the missile assumes a dynamiccondition to maintain its stability While transcending that portion ofthe body of water having wave motion.

5. An apparatus comprising:

(a) a reaction powered missile capable of being launched from a body ofwater having wave motion;

(b) said missile having a nose end and an exhaust nozzle end;

(c) a buoyant member connected to said missile and having suflicientbuoyancy for supporting the missile in a freely suspended position inthe water;

(d) a flexible line which is connected at one end to the buoyant memberand connected at the other end to the nose end of said missile;

(e) said position being at a depth where the nose end is a predetermineddistance below the surface of the water and the nozzle end is spacedabove the bottom of the body of water;

(1'') the missile when suspended being at a depth where the wave motionwill have substantially no effect on its launching stability;

(g) means connected to and extending transverse the missile beyond itssides for dampening vertical movement of the missile when suspended inthe water;

(h) means for releasing the dampening means upon firing the missile;

(i) means for firing the missile when suspended at said depth; and

(j) means for releasing the buoyant member from the missile upon firing,whereby prior to launch and while suspended the missile has suflicientstability for launch, and upon launch the missile assumes a dynamiccondition sufficient to maintain its stability while transcending thatportion of the body of water having wave motion.

6. An apparatus comprising:

(a) an elongate reaction powered missile which is capable of beinglaunched from a body of water having wave motion;

([2) said missile having a nose end and an exhaust nozzle end;

(c) a circular plate connected to the nozzle end and extendingtransverse the missile beyond its sides so as to dampen verticalmovement of the missile when it is disposed upright within the water;

(d) the missile and said circular plate having an aggregate specificgravity greater than one with respect to the water;

(e) a spherical float constructed of a resilient material which hassufiicient buoyancy to float the entire apparatus in the water with aportion of the float extending above the surface of the water;

(f) an elongate flexible line connected atone end to the float andconnected at the other end to the nose end of said missile;

(g) said line being capable of supporting the missile in a freelysuspended position directly within the water with the nose end above thenozzle end;

(11) said line having a length which is capable of positioning the noseend a predetermined distance below the surface of the water with thenozzle end spaced above the bottom of the body of water;

(i) the length of said line further being such that the missile will besuspended at a depth where wave motion will have substantially no effecton launching stability of the missile;

(j) means for firing the missile when suspended at said depth;

(k) means responsive to the firing means for releasing the line and theplate from the missile at the time of firing, whereby prior to launchand while suspended the missile has sufficient stability for launch, andupon launch the missile assumes a dynamic condition to maintain itsstability while transcending that portion of the body of water havingwave motion.

7. An apparatus comprising:

(a) a reaction powered missile which is capable of being launched from abody of water having wave motion;

(b) said missile having a nose end and an exhaust nozzle end;

(c) means for positioning the missile in the water with its nose endabove its nozzle end;

(d) means separably attached to the missile for dampening verticalmovement of the missile when it is positioned within the water; saidmeans for dampening having an opening therein to permit escape ofexhaust gases emanating from said missile upon launch thereof;

(2) means for firing the missile while positioned in the water; and

(7) means for separating the dampening means at the time of firing,whereby the dampening means minimizes vertical movement of the missilewhile positioned in the water and is separated from the missile uponfiring so as to increase eificiency of the missile after launch.

8. An apparatus comprising:

(a) a reaction powered missile which is capable of being launched from abody of water having wave motion;

(b) said missile having a nose end and an exhaust nozzle end;

(c) means for positioning the missile in the water with its nose endabove its nozzle end;

(d) a plate mounted at the nozzle end of the missile and extendingtransverse beyond the sides of the missile for dampening verticalmovement of the missile when the missile is positioned in the Water;said plate separably attached to said missile in watertight relationshiptherewith; said plate having an opening to permit discharge of exhaustgas gases upon launch of said missile;

(e) means for firing the missile While positioned in the water; and

(f) means for separating the dampening means at the time of firing,whereby the dampening means minimizes vertical movement of the missilewhile positioned in the water and is separated from the missile uponfiring so as to increase efiiciency of the missile after launch.

References Cited by the Examiner UNITED STATES PATENTS 6/17 Schneider102-13 3/29 Browne 1023 2/63 Draim et a1 89-1.7 6/ 63 Draim et a1 891.7

BENJAMIN A. BORCHELT, Primary Examiner. SAMUEL W. ENGLE, Examiner.

UNITED STATES PATENT OFFICE CERTIFICATE OF CORRECTION Patent Not3,180,225 April 27, 1965 John Emery Draim It is hereby certified thaterror appears in the above numbered patent requiring correction and thatthe said Letters Patent should read as corrected below.

Column 6, line 52, strike out "an aggregate specific gravity greaterthan one with" and insert instead in a freely suspended positiondirectly within the Signed and sealed this 5th day of October 1965.

(SEAL) A llest:

ERNEST W. SWIDER EDWARD J. BRENNER Attcsting Officer Commissioner ofPatents

1. AN APPARATUS COMPRISING: (A) A REACTION POWERED MISSILE WHICH IS TOBE LAUNCHED FROM A BODY OF WATER HAVING WAVE MOTION; (B) SAID MISSILEHAVING A NOSE END AND AN EXHAUST NOZZLE END; (C) A BUOYANT MEMBER HAVINGSUFFICIENT BUOYANCY TO FLOAT THE ENTIRE APPARATUS IN THE WATER WITH APORTION OF THE BUOYANT MEMBER EXTENDING ABOVE THE SURFACE OF THE WATER;(D) MEANS CONNECTING SAID MISSILE TO SAID BUOYANT MEMBER; SAID MEANSINCLUDING A MEMBER WHICH IS RELEASABLY MOUNTED IN SAID MISSILE; SAIDMEMBER ADAPTED TO BE FORCIBLY EXPELLED FEROM SAID MISSILE UPON LAUNCHTHEREOF; (E) ALL OF THAT PORTION OF THE APPARATUS WHICH IS CONNECTED TOSAID BUOYANT MEMBER HAVING AN AGGREGATE SPECIFIC GRAVITY GREATER THANONE WITH RESPECT TO THE WATER;